CN101750545B - Electromagnetic compatibility test method for electric propulsion system - Google Patents
Electromagnetic compatibility test method for electric propulsion system Download PDFInfo
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- CN101750545B CN101750545B CN2009102425005A CN200910242500A CN101750545B CN 101750545 B CN101750545 B CN 101750545B CN 2009102425005 A CN2009102425005 A CN 2009102425005A CN 200910242500 A CN200910242500 A CN 200910242500A CN 101750545 B CN101750545 B CN 101750545B
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Abstract
An electromagnetic compatibility test method for electric propulsion system comprises the following steps: wave transparent rate of wave transparent subsidiary cabins of electric propulsion system is measured; steady state and transient state electric field radiation of electric propulsion system and steady state power line conducted emission are measured; spike of power line when electric propulsion system is in transient state working condition is measured; conduction of fictitious load and radiation emission characteristic and actual thrustor are compared and measured; influence of plume to communication is measured to obtain electromagnetic compatibility test data of electric propulsion system. The inventive method is not required to be carried out in an electromagnetic compatibility laboratory, and can be tested on out-field or working site of electric propulsion system, the test result has little error and can authentically reflect electromagnetic compatibility of the propulsion system, thus greatly lowering test cost and improving working efficiency.
Description
Technical field
The present invention relates to the electromagnetic compatibility test method of electric propulsion system, be applicable in amateur electromagnetic compatibility laboratory and finish, can obtain comparatively real test data, belong to the satellite propulsion system field tests.
Background technology
At present, the general employing of Chang Yong satellite propulsion system is chemical propulsion system and electric propulsion system.And China generally uses chemical propulsion system, does not also have satellite to adopt electric propulsion system to make the thrust of satellite.
Electric propulsion system mainly comprises: vacuum tank, the secondary cabin of saturating ripple, thruster.The mutual electromagnetic influence of other subsystem electronic equipments of electric propulsion system and satellite, comprise conduction and radiation two classes, both comprised the influence of electric propulsion device conduction and Radiation Emission, also comprised the influence of the conduction of other subsystem electronic equipments of satellite and Radiation Emission electric propulsion system to other subsystem electronic equipments of satellite.Obtain the Electro Magnetic Compatibility data of electric propulsion system, analyze its whether with other hardware compatibility work of satellite, the reply electric propulsion system carries out electromagnetic compatibility test.The electric propulsion device need be worked in vacuum environment, need place it in to carry out correlation test in the vacuum tank.The test of at present external electric propulsion system is carried out in the electromagnetic compatible dark chamber of specialty, cost is higher, the electromagnetic compatible dark chamber of this specialty is special in cooperating electric propulsion system to carry out electromagnetic compatibility test, obtain the Electro Magnetic Compatibility data of electric propulsion system and build, these characteristics show the placement location of vacuum tank, and detection signal spreads out of the signal interface board of screened room, the Position Design that the measurement antenna is placed etc.The vacuum system of China's employing at present can't enter carries out electromagnetic compatibility test in the shielded anechoic chamber, therefore can only in the outfield, carry out EMC test, affected by environment, the test result error that adopts traditional electromagnetic compatible testing method to obtain is bigger, can't truly reflect the Electro Magnetic Compatibility of propulsion system.
Summary of the invention
The problem that the technology of the present invention solves is: overcome the deficiencies in the prior art, a kind of electromagnetic compatibility test method of electric propulsion system is provided, this method need not carried out in testing laboratory, directly in the outfield or the scene test, the test result error is little, the Electro Magnetic Compatibility that can truly reflect propulsion system, and it is low to have saved cost greatly, has improved work efficiency.
Technical solution of the present invention: the electromagnetic compatibility test method of electric propulsion system comprises: the saturating ripple rate in the secondary cabin of saturating ripple of electric propulsion system is measured; The electric field radiation of electric propulsion system stable state, transient state and steady state power line conduction emission measurement; Electric propulsion system is under transient condition, and the spiking of power lead is measured; Comparing and measuring of the conduction of fictitious load and Radiation Emission characteristic and actual thrustor; Plume is measured the communication influence, obtains the electromagnetic compatibility test data of electric propulsion system, wherein:
(1) the saturating ripple rate measuring method in the secondary cabin of saturating ripple of electric propulsion system is: saturating ripple rate obtains by relative method, be about to the inside and outside both sides that dual-mode antenna is placed on the secondary cabin of ripple respectively, the plasma transmission situation of in whole electric propulsion system, spraying behind the secondary cabin of the saturating ripple of measurement result acquisition electromagnetic wave process by vector network analyzer fl transmission coefficient, promptly saturating ripple pair cabin transport property; Again dual-mode antenna is placed in the barnyard, distance between the dual-mode antenna distance relative with the previous step dual-mode antenna is identical, without any object, measures by the fl transmission coefficient of vector network analyzer between the antenna again, the data of measuring are as the reference data, i.e. the reference transmission characteristic; The transmission data and the reference transmission data in the secondary cabin of saturating ripple are carried out the processing of time domain door respectively, and relatively twice measurement result obtains the influence of the secondary cabin of ripple for electromagnetic wave propagation, promptly obtains the saturating ripple rate in the secondary cabin of ripple;
(2) Radiation Emission of electric propulsion system stable state and power lead conduction emission measurement method are:
(2.1) the electric field radiation emission measurement method of electric propulsion system stable state is: when electric propulsion system is in the steady operation pattern, antenna is placed on the outside in the secondary cabin of ripple, the secondary cabin of the saturating ripple of distance 1m distance, antenna height is aimed at the watch window in the secondary cabin of ripple, antenna is connected to the input port of receiver by cable, gather electric propulsion system electric field radiation emission data at this moment by receiver, promptly obtain the electric field radiation emssion characteristic curve of electric propulsion system stable state;
(2.2) the conduction emission measurement method of electric propulsion system stable state is: linear impedance stabilization network is connected between power supply processing unit and the electric thruster, the signal output part of linear impedance stabilization network is connected to the input port of receiver, gather electric propulsion system power lead conduction emission data at this moment by receiver, promptly obtain electric propulsion system steady state power line conduction emssion characteristic curve;
(3) the electric field radiation emission measurement method of electric propulsion system transient state is: the electric field radiation that receives the generation of electric propulsion system transient working by antenna transmits, receiver or frequency spectrograph carry out real-time frequency domain characteristic and measure, transient electric field radiation emission measurement frequency range is 10kHz-5GHz, in the 10kHz-5GHz frequency range, use respectively bar antenna as 10kHz-30MHz, biconical antenna as 30MHz-200MHz, log-periodic antenna as 200MHz-1GHz, double-ridged horn antenna receiving antenna as the 1GHz-5GHz frequency range.The operating mode of electric propulsion system transient state is respectively: negative electrode heating, neutralizer igniting, arc chamber discharge, draw four operating modes of line.Before each transient condition begins to measure, make the ground checkout equipment work of electric propulsion system earlier, electric propulsion system is not worked, under this kind operating mode, carry out the data acquisition of on-the-spot 10kHz-5GHz electric field environment, these data are referred to as background data, after background data was gathered, setting electric propulsion system was the transient working pattern of appointing, carries out the transient electric field radiation emission measurement of electric propulsion system.Each transient condition of electric propulsion system all will be finished the measurement of 10kHz-5GHz frequency range, and when carrying out each frequency range test, each operating mode will continue 15-20 minute.That is, in 15-20 minute, the action that requires the function change-over switch of electric propulsion system not stop is arranged to the transient working pattern, as negative electrode heating mode etc.Receiver, frequency spectrograph carry out the maximum envelope measurement pattern that keeps at this moment, and the electric field radiation that obtains transient condition this moment is launched data.The electric field radiation emission data of this moment and the background data that records are previously compared, weed out the signal that produces when not belonging to the electric propulsion system transient working in the background environment, obtain the electric field radiation emission measurement result of electric propulsion system under four kinds of transient conditions respectively.
(4) electric propulsion system is under transient condition, the spiking measuring method of power lead: directly be connected by oscillographic voltage probe on the power supply supply lines of electric propulsion system, catch the spiking that electric propulsion system produces on the power lead under transient condition;
(5) conduction of fictitious load and Radiation Emission characteristic compare and measure method with true angle of rake: at first need to set the load identical with the electric propulsion system electrical characteristics, i.e. a fictitious load; The electric field radiation that fictitious load is carried out under stable state and the transient condition is launched and conduction emission measurement then, and the power lead spiking is measured under the transient state; With with measure identical measurement project and the method for actual thrustor, do not contain the influence of plume at this to communication.After the measurement of finishing true electric propulsion system, the power supply processing unit disconnects with actual thrustor and being connected, and is connected with fictitious load.Make and flow through the electric current identical on the power lead with actual thrustor.After finishing the fictitious load measurement, according to each measurement project, the measurement result of actual thrustor and the measurement result of fictitious load are compared, understand the difference of the Electro Magnetic Compatibility characteristic of fictitious load and actual thrustor, in order to estimate fictitious load when replacing true electric propulsion system and whole star joint test, whether test mode can fully represent actual thrustor.
(6) measuring method of plume to communicating by letter and influencing: the electric propulsion device is under different power voltage and electric current, the plume that is produced can be different, supply voltage influences the ion velocity of plume, supply current influences the ion concentration of plume, need measure the influence of communication different voltages and plume that currents combination produced, promptly carry out plume under 15 kinds of different operating states the influence of communication is measured, the surveying work state sees the following form
| Duty | Supply voltage | Supply current | Duty | Supply | Supply current | |
| 1 | 1000V | 0.8A | 9 | 1000V | 0.9 |
|
| 2 | 1100V | 0.8 |
10 | | 1A | |
| 3 | 1200V | 0.8A | 11 | 1000V | 1.1 |
|
| 4 | 1300V | 0.8A | 12 | 1000V | 1.2 |
|
| 5 | 1400V | 0.8A | 13 | 1000V | 0.7 |
|
| 6 | 1500V | 0.8A | 14 | 1000V | 0.6A | |
| 7 | 900V | 0.8A | 15 | 0V | 0A | |
| 8 | 800V | 0.8A |
Under every kind of duty, receive and launch on the observation panel that two antenna actinal surfaces are attached to the secondary cabin of ripple, receive and launch two antenna actinal surfaces and point to relatively, make plume pass electromagnetic wave transmission path; Receive and launch two antennas and be connected to vector network analyzer by cable respectively, obtain the transmission situation of the whole electric propulsion system link of reaction from the measurement result of the fl transmission coefficient of vector network analyzer, contrast the influence of plasma plume under 15 kinds of different operating states transmitting; At last test result is carried out range gate and handle, finally estimated the result that influences of plume communication.
The method specific implementation of described time domain door is: carry out sweep check by antenna and receiver, obtain the frequency curve data, again the frequency curve data are carried out Fourier transform and obtain time-domain spectral, determine by time series analysis, the garbage signal of test site is picked out, again this partial data is carried out the saturating ripple rate that Fourier transform obtains the final secondary cabin of saturating ripple.
The method specific implementation of described range gate is: carry out sweep check by antenna and receiver, obtain the frequency curve data, again the frequency curve data are carried out Fourier transform and obtain time-domain curve, the transverse axis time variable of time-domain curve be multiply by light velocity C=3 * 10
8M/s obtains the damping capacity of test macro on different transmission path, estimates the influence of plume to communication with this.
The present invention's advantage compared with prior art is:
(1) test event and the measuring method of the present invention by choosing estimated the electromagnetic compatibility characteristic of domestic electric propulsion system first.The electromagnetic compatibility characteristic comprises the electric field radiation emission characteristics of electric propulsion system stable state and transient state and the power lead spiking characteristic of transient state.From of the influence of these specificity analysis electric propulsion systems to the generation of satellite on-board equipment.Test result has very big consistance with external measurement result simultaneously.
(2) place of measuring method of the present invention need not carried out in the laboratory, be applicable in the non-screened room and finish, direct like this in the outfield or the scene test, the test result error is little, comparatively real test data can be obtained, the Electro Magnetic Compatibility of propulsion system can be truly reflected.
(3) the present invention has estimated the influence of plume to communicating by letter in the electric propulsion system first.
(4) the present invention has improved the electromagnetic compatibility test ability of domestic electric propulsion system, for whole star electromagnetic Compatibility Design data provide strong technical support, has stepped major step again forward for realizing the widespread use of electric propulsion device on whole star system.
(5) this method of the present invention need not carried out in the electromagnetic compatibility laboratory of specialty, directly in the outfield or the scene of electric propulsion system work test, the test result error is little, the Electro Magnetic Compatibility that can truly reflect propulsion system, and reduced experimentation cost significantly, improved work efficiency.
Description of drawings
Fig. 1 is the chief component block diagram of electric propulsion system;
Fig. 2 is that the saturating ripple rate in the secondary cabin of ripple of the present invention is measured block diagram;
Fig. 3 is the electric field radiation emission measurement block diagram of electric propulsion system stable state of the present invention and transient state;
Fig. 4 is a steady state power line conduction emission measurement block diagram of the present invention;
Fig. 5 is that the power lead spiking of electric propulsion system transient state of the present invention is measured block diagram;
Fig. 6 measures block diagram for plume of the present invention to the influence of communication;
Fig. 7 is the measurement result of the saturating ripple rate of the secondary cabin 200MHz-1GHz of the saturating ripple of the present invention;
Fig. 8 is the measurement result of the saturating ripple rate of the secondary cabin 200MHz-1GHz of the saturating ripple of the present invention;
Fig. 9 is electric propulsion system stable state of the present invention and fictitious load steady-state field radiation emission measurement result;
Figure 10 is electric propulsion system actual thrustor stable state of the present invention and fictitious load power lead conduction emission measurement result;
Figure 11 is a plume transport property of the present invention, i.e. the influence of plume to communicating by letter under the electric propulsion system different power voltage;
Figure 12 is a plume transport property of the present invention, i.e. the influence of plume to communicating by letter under the different supply currents of electric propulsion system.
Embodiment
As shown in Figure 1, electric propulsion system is mainly by vacuum tank 1, the secondary cabin 2 of saturating ripple, each frequency range electric field receiving antenna 5, power supply processing unit and electric thruster 6, electricity thruster 6 is installed in the secondary cabin 2 of ripple, the electricity thruster is by the power supply of power supply processing unit, the electricity thruster is fixed in the secondary cabin of ripple by ring flange, and vacuum tank is connected by ring flange with the secondary cabin of saturating ripple.For making the electric propulsion system can operate as normal, at first to vacuumize, make vacuum tank 1 reach certain vacuum tightness.Through switch motion, make electric propulsion system be in steady-working state, plasma is in stable spray regime, i.e. the steady-working state of electric propulsion system.Electric propulsion system is installed on the satellite, becomes satellite propulsion system.In the process of the control attitude of satellite and track, four transient conditions are arranged: first operating mode, negative electrode heating by being closed to operate as normal; Second operating mode, the neutralizer igniting; The 3rd operating mode: arc chamber igniting; The 4th operating mode is drawn line; Utilize receiver to carry out the extracting of transient state frequency spectrum and waveform at these several switch motions.
The test event of the electromagnetic compatibility test of electric propulsion system of the present invention has: the saturating ripple rate in the secondary cabin of saturating ripple of (1) electric propulsion system is measured; (2) emission of the electric field radiation of electric propulsion system stable state, transient state and steady state power line conduction emission measurement; (3) electric propulsion system is under transient condition, and the spiking of power lead is measured; (5) conduction of fictitious load and Radiation Emission characteristic and actual thrustor compares and measures; (6) plume is measured the communication influence.
As shown in Figure 2, the saturating ripple rate instrumentation plan in the secondary cabin of saturating ripple of electric propulsion system.The electricity thruster mainly carries out work under vacuum environment, it is fixed in the vacuum tank a certain position and carries out ion and spray, in order in research process, to understand in its course of injection, the electromagnetic property that the related electric system produces, a cabin body part is made as has wave energy, finish the installation and the debugging work of electric propulsion device simultaneously.The staff is a wave penetrate capability of recognizing tank body, be that how many decay electric field radiation emission that what electromagnetic radiation electric propulsion system work the time specifically have be measured fully or measure has been passed through and received by out of my cabin antenna, be called the saturating ripple rate in the secondary cabin of ripple.
The saturating ripple rate measuring method in the secondary cabin of saturating ripple of electric propulsion system is: saturating ripple rate obtains by relative method, is about to receive the inside that antenna is placed on the secondary cabin of ripple, sends out the outside that antenna is placed the secondary cabin of ripple, and antenna height is got 1.2 meters, 1 meter of dual-mode antenna spacing, and actinal surface is relative.The signal testing cable is drawn by secondary cabin of saturating ripple and vacuum tube flange connections.By the plasma transmission situation in the whole electric propulsion system behind the secondary cabin of the saturating ripple of measurement result acquisition electromagnetic wave process of vector network analyzer fl transmission coefficient, promptly saturating ripple pair cabin transport property; Again dual-mode antenna is placed in the barnyard, distance between the dual-mode antenna distance relative with the previous step dual-mode antenna is identical, between the antenna without any object, measure by the fl transmission coefficient of vector network analyzer again, the data of measuring are as the reference data, it is the reference transmission characteristic, the transport property in the secondary cabin of saturating ripple and reference transmission family curve all need to carry out the time domain door to be handled, be about to frequency curve and obtain time-domain curve by the Fourier variation, on time-domain curve, differentiate the signal of different transmission path, the signal of these different transmission path comprises the repeatedly reflected signal in needed direct wave signal and the in-site measurement environment, as the direct wave transmission time be 0.1ns, and repeatedly the transmission time of reflected signal all greater than 0.2ns, on time-domain curve, weed out undesired signal, then rejected the interference of environment measuring greater than the environment generation of 0.2ns.Data after again two groups being handled well compare, and have both obtained the influence of the secondary cabin of ripple for electromagnetic wave propagation, the saturating ripple rate in the secondary cabin of promptly saturating ripple; According to the measurement requirement of electric field radiation emission, need finish the measurement of 200MHz-5GHz frequency range, in requisition for the data that obtain the secondary cabin of saturating ripple saturating ripple rate in the 200MHz-5GHz frequency range.The wave penetrate capability of 200MHz～1GHz frequency range can reach more than 70%, 1GHz～5GHz can reach more than 80%, the radiation emission test result will be than about the little 1dB of real Radiation Emission, the saturating ripple rate 1dB in the secondary cabin of promptly saturating ripple, and the measurement result curve is seen Fig. 7 and Fig. 8.
As shown in Figure 3, electric propulsion system stable state and transient electric field radiation emission measurement block diagram.
Electric propulsion system is when steady operation, and related electric equipment carries out work, and these electrical equipments can produce electric field radiation and transmit, i.e. the electric field radiation of electric propulsion system stable state emission.Satellite is in flight and carry out attitude, track need carry out electric propulsion system when adjusting and finish Thrust Control, electric propulsion system has a series of switch motion when carrying out work, these switches can produce electric field radiation and transmit in course of action, i.e. the electric field radiation of transient state emission.
The electric field radiation emission measurement method of electric propulsion system stable state is: when electric propulsion system is in the steady operation pattern, successively respectively the measurement antenna of different frequency range is placed on the outside in the secondary cabin 2 of ripple, the distance in the secondary cabin 2 of the saturating ripple of distance is 1m, antenna height is aimed at the watch window in the secondary cabin 2 of ripple, antenna is connected to the input port of receiver by cable, gather electric propulsion system electric field radiation emission data, i.e. the electric field radiation emssion characteristic curve of electric propulsion system stable state at this moment by receiver.The measurement frequency range is 200MHz-5GHz, and satellite is paid close attention to the working frequency range that frequency range is receiver on the satellite star.At this moment, what need especially to pay close attention to is receiving belt on the satellite star, whether understanding has signal to fall into band in the receiving belt of satellite, estimates the interference whether receiving equipment on the satellite star receives electric propulsion system with this electric field radiation emission angle from electric propulsion system.Shown in the test result tabulation 1, test curve is seen Fig. 9.
The electric field radiation emission measurement result of table 1 electric propulsion system stable state
| Frequency range | Test result |
| 200MHz-1GHz | Be lower than near 70dB μ V/m (wherein signal is lower than 89dB μ V/m 900MHz, and analyzing its signal is mobile phone signal, therefore gets rid of this signal) |
| 1GHz-5GHz | Have more some than background at 2.4-3.6GHz and exceed envelope about noise spectrum 12dB. |
| 1.574GHz-1.576GHz | Have the 1.574GHz signal to send, be lower than 12dB μ V/m, (not having this signal in the background) meets the demands |
| 2.025GHz-2.1GHz | 2.061GHz exceed requirement 2dB, amplitude is 31.99dB μ V/m.(not having this signal in the background) |
| 2.1GHz-2.3GHz | Be lower than 30dB |
| 2.4GHz-2.5GHz | Almost consistent with background, be difficult to the quantitative identification signal magnitude. |
The electric field radiation emission measurement method of electric propulsion system transient state is: the electric field radiation that receives the generation of electric propulsion system transient working by antenna transmits, receiver or frequency spectrograph carry out real-time frequency domain characteristic and measure, transient electric field radiation emission measurement frequency range is 200MHz-5GHz, biconical antenna as 30MHz-200MHz, log-periodic antenna as 200MHz-1GHz, double-ridged horn antenna receiving antenna as the 1GHz-5GHz frequency range.Above-mentioned each antenna is placed on a side in the secondary cabin of ripple, the secondary cabin 1m of the saturating ripple of distance, antenna height 1.2m.The operating mode of electric propulsion system transient state is respectively: negative electrode heating, neutralizer igniting, arc chamber discharge, draw four operating modes of line.Before each transient condition begins to measure, make the ground checkout equipment work of electric propulsion system earlier, electric propulsion system is not worked, under this kind operating mode, carry out the data acquisition of on-the-spot 200MHz-5GHz electric field environment, these data are referred to as background data, after background data was gathered, setting electric propulsion system was the transient working pattern of appointing, carries out the transient electric field radiation emission measurement of electric propulsion system.Each transient condition of electric propulsion system all will be finished the measurement of 200MHz-5GHz frequency range, when carrying out each frequency range test, each operating mode will continue 15-20 minute, promptly in 15-20 minute, the action that the function change-over switch of requirement electric propulsion system is not stopped, be arranged to the transient working pattern, as negative electrode heating mode etc.Receiver, frequency spectrograph carry out the maximum envelope measurement pattern that keeps at this moment, and the electric field radiation that obtains transient condition this moment is launched data.This test is to carry out in non-screened room, during this period of time the data result of Ce Lianging has not only comprised the electric field radiation emission of electric propulsion system transient state switch motion, other irrelevant electromagnetic environments in the site environment have also been comprised, which needs to distinguish is that the electric field radiation that the electric propulsion system transient working produces transmits, adopt comparative approach, weed out the signal that produces when not belonging to the electric propulsion system transient working in the background environment, obtain the electric field radiation emission measurement result of electric propulsion system under four kinds of transient conditions respectively.The measurement result of electric propulsion system transient electric field Radiation Emission sees Table 2, and difference is little as a result for the electric field radiation emission measurement of the transient state of fictitious load and actual thrustor.
Table 2 electric propulsion system transient electric field radiation emission measurement result
As shown in Figure 4, the conduction emission measurement method of electric propulsion system stable state is: linear impedance stabilization network is connected in power supply processing unit and the electric propulsion system, be connected the input port of receiver by the signal output port of linear impedance stabilization network, gather electric propulsion system power lead conduction emission data at this moment, the i.e. power lead of electric propulsion system conduction emssion characteristic curve by receiver.
Actual thrustor at 10kHz-1MHz, will exceed 25dB, 15dB near the 4MHz than fictitious load.The emission maximum frequency spectrum is near the 300kHz, and the emission amplitude is 95dB μ V.The live wire of real load is consistent with zero line conduction emission results, and the live wire of fictitious load is consistent with zero line conduction emission results.The steady state power line conduction emission measurement curve of actual thrustor and fictitious load is seen Figure 10.
As shown in Figure 5, electric propulsion system is under transient condition, and the spiking of power lead is measured block diagram.Because the switching of the variation of electric current and switch can produce conduction transmits, promptly be called transient peak signal conduction emission on the power lead of electric propulsion device.
Electric propulsion system is under transient condition, and it is as follows that the spiking of power lead is measured: on the positive and negative power supply supply lines that directly is connected electric propulsion system of oscillographic probe, catch electric propulsion system spiking on the power lead under transient condition.Spiking conduction emission measurement on the power lead of electric propulsion system the results are shown in following table 3.The electric propulsion system transient condition is respectively: line is lighted a fire, drawn to negative electrode heating, neutralizer igniting, arc chamber.When being transformed into fictitious load when connecting, according to the characteristic of fictitious load, the transient condition of fictitious load is respectively: two negative electrodes open, two negative electrodes close, draw line and irritate, draw the line grid of spreading its tail and open, draw line and quicken to open.Spiking conduction emission measurement on the fictitious load power lead the results are shown in Table 4.
Spiking conduction emission measurement result on the power lead of table 3 electric propulsion system
Spiking conduction emission measurement result on the table 4 fictitious load power lead
As shown in Figure 5, comparing and measuring of the conduction of fictitious load and Radiation Emission characteristic and real load is as follows: at the research initial stage of electric propulsion system, electric propulsion system can not reality be participated in the joint test of each satellite system, need a known load, the electrical characteristics of its characteristic and electric propulsion system identical, be called fictitious load.Whether can replace true electric propulsion system to participate in later research and test for understanding fictitious load, the measurement project that fictitious load is carried out has: electric field radiation emission and conduction emission measurement under stable state and the transient condition, the power lead spiking is measured.
Compare by the measurement result of carrying out electric propulsion system steady-state field Radiation Emission, stable state power lead conduction emission, transient electric field Radiation Emission, transient state power lead spiking conduction emission measurement project and fictitious load, (10kHz～1MHz), electric propulsion system exceeds 25dB～30dB than fictitious load on amplitude for the real load of thruster and the power lead of fictitious load conduction emission low-frequency range.The electric propulsion system mxm. is about 270kHz, and amplitude is no more than 100dB μ V.The emission amplitude of electric propulsion system is below 100dB μ V/m.Fictitious load is in the emission amplitude of the little 20dB of the minimum meeting of low frequency 10kHz-200kHz.Electric propulsion system has plume to take place, and can whole noise be improved 10dB.Real load and the fictitious load measurement result difference on transient state is little.
As shown in Figure 6, plume is to the measurement block diagram of communication influence.The electric propulsion device is under different power voltage and electric current, and the plume that is produced can be different, and supply voltage influences the ion velocity of plume, and supply current influences the ion concentration of plume.Need measure the influence of communication different voltages and plume that currents combination produced.Promptly carrying out plume under the different operating state measures the influence of communication.Being arranged in the influence measurement of plume to communication of different voltages of electric propulsion system and electric current has 15 kinds of duties, sees Table 5.The frequency range of measuring should be the working frequency range of the satellite-ground link of satellite.
Table 5: the duty that electric propulsion system was provided with during plume of the present invention was measured the influence of communication
| Duty | Supply voltage | Supply current | Duty | Supply | Supply current | |
| 1 | 1000V | 0.8A | 9 | 1000V | 0.9 |
|
| 2 | 1100V | 0.8 |
10 | | 1A | |
| 3 | 1200V | 0.8A | 11 | 1000V | 1.1 |
|
| 4 | 1300V | 0.8A | 12 | 1000V | 1.2 |
|
| 5 | 1400V | 0.8A | 13 | 1000V | 0.7 |
|
| 6 | 1500V | 0.8A | 14 | 1000V | 0.6A | |
| 7 | 900V | 0.8A | 15 | 0V | 0A | |
| 8 | 800V | 0.8A |
Plume is as follows to the measurement of communication influence: test frequency is 1GHz～5GHz, and emissive power is-5dBm, and number of test points is 3201 points, and intermediate-frequency bandwidth is 500Hz.To receive and dispatch two antennas and be placed on both sides, the secondary cabin of ripple, the two antenna actinal surfaces secondary cabin of ripple of trying one's best to reduce the influence of environment, is received and dispatched two antenna actinal surfaces and is pointed to relatively during test, makes plume pass electromagnetic wave transmission path; Two antennas are connected to vector network analyzer by cable respectively, read the result of fl transmission coefficient from vector network analyzer, react the transmission situation of whole electric propulsion system link, plume transfer curve and supply current changed plume transfer curve down under promptly supply voltage changed.Analyze the influence of plasma plume under 15 kinds of different operating states to transmitting; The duty of electric propulsion system is provided with and mainly comprises supply voltage and supply current.At first supply current is fixed on 0.8A, supply voltage changes to 1500V by 800V, and the change in voltage stepping is 100V, investigates the influence situation of plume to communicating by letter under the different power voltage, obtains supply voltage and changes plume transfer curve down; With supply voltage stuck-at-000V, supply current changes to 1.2A by 0.6A then, and it is 0.1A that electric current changes stepping, investigates the influence situation of plume to communicating by letter under the different supply currents, obtains supply current and changes plume transfer curve down.Because whole test system environment of living in is comparatively complicated, institute's test result not only comprises the direct wave signal, also have the environment spurious signal, therefore need carry out range gate to plume transfer curve under plume transfer curve and supply current change under the supply voltage variation and handle, reduce spuious influence.The range gate processing signals is, transfer curve is obtained the distance domain curve by the Fourier variation, on the distance domain curve, differentiate the signal of different transmission path, the signal of these different transmission path comprises the repeatedly reflected signal in needed direct wave signal and the in-site measurement environment, as the direct wave path-length is the diameter 0.8m in the secondary cabin of ripple, and repeatedly the path-length of reflected signal all greater than 1m, on the distance domain curve, weed out undesired signal, then rejected the interference of environment measuring greater than the environment generation of 1m.Increase with supply voltage, signal transmission path reduces, and phase deviation reduces, and promptly plume diminishes to the influence of communication; Increase with supply current, the signal transmission path decay increases, and phase deviation increases, and promptly plume becomes big to the influence of communication; Along with frequency raises, plume diminishes gradually to the electromagnetic transmission influence.
Measure curve and see Figure 11 and Figure 12, as can be seen, plume has certain influence to communication from test result, but influences less.When replacing real load to put in order the star joint test, can ignore the influence of plume with fictitious load.
The content that is not described in detail in the instructions of the present invention belongs to this area professional and technical personnel's known prior art.
Although disclose most preferred embodiment of the present invention and accompanying drawing for the purpose of illustration, it will be appreciated by those skilled in the art that: without departing from the spirit and scope of the invention and the appended claims, various replacements, variation and modification all are possible.Therefore, the present invention should not be limited to most preferred embodiment and the disclosed content of accompanying drawing.
Claims (3)
1. the electromagnetic compatibility test method of electric propulsion system, it is right to it is characterized in that comprising: the saturating ripple rate in the secondary cabin of the saturating ripple of electric propulsion system is measured; The electric field radiation of electric propulsion system stable state, transient state and electric propulsion system steady state power line conduction emission measurement; Electric propulsion system is under transient condition, and the spiking of power lead is measured; Comparing and measuring of the conduction of fictitious load and Radiation Emission characteristic and actual thrustor; Plume is measured the communication influence, obtains the electromagnetic compatibility test data of electric propulsion system, wherein:
(1) the saturating ripple rate measuring method in the secondary cabin of the saturating ripple of electric propulsion system is: saturating ripple rate obtains by relative method, be about to the inside and outside both sides that dual-mode antenna is placed on the secondary cabin of ripple respectively, the plasma transmission situation of in whole electric propulsion system, spraying behind the secondary cabin of the saturating ripple of measurement result acquisition electromagnetic wave process by vector network analyzer fl transmission coefficient, promptly saturating ripple pair cabin transport property; Again dual-mode antenna is placed in the barnyard, distance between dual-mode antenna is identical with distance between the previous step dual-mode antenna, without any object, measures by the fl transmission coefficient of vector network analyzer between the antenna again, the data of measuring are as the reference data, i.e. the reference transmission characteristic; The transmission data and the reference data in the secondary cabin of saturating ripple are carried out the processing of time domain door respectively, and relatively twice measurement result obtains the influence of the secondary cabin of ripple for electromagnetic wave propagation, promptly obtains the saturating ripple rate in the secondary cabin of ripple;
(2) Radiation Emission of electric propulsion system stable state and power lead conduction emission measurement method
(2.1) the electric field radiation emission measurement method of electric propulsion system stable state is: when electric propulsion system is in the steady operation pattern, antenna is placed on the outside in the secondary cabin of ripple, the secondary cabin of the saturating ripple of distance 1m distance, antenna height is aimed at the watch window in the secondary cabin of ripple, antenna is connected to the input port of receiver by cable, gather electric propulsion system electric field radiation emission data at this moment by receiver, promptly obtain the electric field radiation emssion characteristic curve of electric propulsion system stable state;
(2.2) the conduction emission measurement method of electric propulsion system stable state is: linear impedance stabilization network is connected between power supply processing unit and the electric thruster, the signal output part of linear impedance stabilization network is connected to the input port of receiver, gather electric propulsion system power lead conduction emission data at this moment by receiver, promptly obtain electric propulsion system steady state power line conduction emssion characteristic curve;
(3) the electric field radiation emission measurement method of electric propulsion system transient state is: the electric field radiation that receives the generation of electric propulsion system transient working by antenna transmits, receiver or frequency spectrograph carry out real-time frequency domain characteristic and measure, transient electric field radiation emission measurement frequency range is 200MHz-5GHz, biconical antenna as 30MHz-200MHz, log-periodic antenna as 200MHz-1GHz, double-ridged horn antenna receiving antenna as the 1GHz-5GHz frequency range; The operating mode of electric propulsion system transient state is respectively: negative electrode heating, neutralizer igniting, arc chamber discharge, draw four operating modes of line; Before each transient condition begins to measure, make the ground checkout equipment work of electric propulsion system earlier, electric propulsion system is not worked, under this kind operating mode, carry out the data acquisition of on-the-spot 10kHz-5GHz electric field environment, these data are referred to as background data, after background data was gathered, setting electric propulsion system was the transient working pattern of appointing, carries out the transient electric field radiation emission measurement of electric propulsion system; Each transient condition of electric propulsion system all will be finished the measurement of 10kHz-5GHz frequency range, when carrying out each frequency range test, each operating mode will continue 15-20 minute, promptly in 15-20 minute, the transient condition pattern is arranged in the action that the function change-over switch of requirement electric propulsion system is not stopped; This moment, receiver or frequency spectrograph carried out the maximum envelope measurement pattern that keeps, and obtained the electric field radiation emission data of transient condition this moment; The electric field radiation emission data of this moment and the background data that records are previously compared, weed out the signal that produces when not belonging to the electric propulsion system transient working in the background environment, obtain the electric field radiation emission measurement result of electric propulsion system under four kinds of transient conditions respectively;
(4) electric propulsion system is under transient condition, the spiking measuring method of power lead: directly be connected by oscillographic voltage probe on the power supply supply lines of electric propulsion system, catch the spiking that electric propulsion system produces on the power lead under transient condition;
(5) conduction of fictitious load and Radiation Emission characteristic compare and measure method with true angle of rake: at first need to set the load identical with the electric propulsion system electrical characteristics, i.e. a fictitious load; The electric field radiation that fictitious load is carried out under stable state and the transient condition is launched and conduction emission measurement then, and the power lead spiking is measured under the transient state; With with measure identical measurement project and the method for actual thrustor, do not contain the influence of plume at this to communication; After the measurement of finishing true electric propulsion system, the power supply processing unit disconnects with actual thrustor and being connected, and is connected with fictitious load, makes and flows through the electric current identical with actual thrustor on the power lead; After finishing the fictitious load measurement, according to each measurement project, the measurement result of actual thrustor and the measurement result of fictitious load are compared, understand the difference of the Electro Magnetic Compatibility characteristic of fictitious load and actual thrustor, in order to estimate fictitious load when replacing true electric propulsion system and whole star joint test, whether test mode can fully represent actual thrustor;
(6) measuring method of plume to communicating by letter and influencing: the electric propulsion device is under different power voltage and electric current, the plume that is produced can be different, supply voltage influences the ion velocity of plume, supply current influences the ion concentration of plume, need measure the influence of communication different voltages and plume that currents combination produced, promptly carry out plume under 15 kinds of different operating states the influence of communication is measured, the surveying work state sees the following form
Under every kind of duty, receive and launch on the observation panel that two antenna actinal surfaces are attached to the secondary cabin of ripple, receive and launch two antenna actinal surfaces and point to relatively, make plume pass electromagnetic wave transmission path; Receive and launch two antennas and be connected to vector network analyzer by cable respectively, obtain the transmission situation of the whole electric propulsion system link of reaction from the measurement result of the fl transmission coefficient of vector network analyzer, contrast the influence of plasma plume under 15 kinds of different operating states transmitting; At last test result is carried out range gate and handle, finally estimated the result that influences of plume communication.
2. the electromagnetic compatibility test method of electric propulsion system according to claim 1, it is characterized in that: the method specific implementation of described time domain door is: carry out sweep check by antenna and receiver, obtain the frequency curve data, again the frequency curve data are carried out Fourier transform and obtain time-domain spectral, determine by time series analysis, the garbage signal of test site is picked out, again this partial data is carried out the saturating ripple rate that Fourier transform obtains the final secondary cabin of saturating ripple.
3. the electromagnetic compatibility test method of electric propulsion system according to claim 1, it is characterized in that: the method specific implementation of described range gate is: carry out sweep check by antenna and receiver, obtain the frequency curve data, again the frequency curve data are carried out Fourier transform and obtain time-domain curve, the transverse axis time variable of time-domain curve be multiply by light velocity C=3 * 10
8M/s obtains the damping capacity of test macro on different transmission path, estimates the influence of plume to communication with this.
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